Results
98-16-18: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Learjet Model 60 airplanes. This action requires repetitive measurements of the brake wear dimension between the housing subassembly and the pressure plate that is adjacent to the top pistons of the brake assembly; and follow-on corrective actions, if necessary. This amendment is prompted by reports of abnormal (uneven) brake wear. The actions specified in this AD are intended to detect and repair an abnormal brake wear condition, which could result in loss of brake effectiveness and cause the airplane to leave the runway surface.
2011-08-07: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: In January 2009 a Trent 895 powered Boeing 777-200 aircraft experienced release of a low pressure (LP) compressor blade which failed due to fatigue cracking in the root section of the blade. The released blade (undercut root standard) had received a part life processing to apply a compression layer to the blade root (Service Bulletin SB 72-D672--Introduction of Laser Shock Peening (LSP)) and also a part life upgrade to the retention feature lubrication system. Investigation has revealed that the effectiveness of this upgraded blade root lubrication coating system may be reduced dependant on the extent of previous running with the earlier standard, leadingto increased blade root stress levels. In the specific case of the released blade, a review of its in-service modification history has shown that it operated for a relatively high number of flight cycles prior to the compression layer processing and the new retention feature lubrication system. A review of the Engine Health Monitoring data has also identified it operated at high N1 speeds compared to the Trent 800 fleet average N1 speeds. The combination of these factors has resulted in increased fatigue life usage which is considered to have led to crack initiation and propagation prior to reaching the blades declared life limit. A review of all in-service undercut/LSP standard Trent 800 LP compressor blades has identified specific blades that carry a similar increased susceptibility to cracking. This AD is issued to mitigate the risk of possible multiple fan blades failure affecting those blades identified as described above which could lead to high energy non contained debris from the engine. We are issuing this AD to prevent LP compressor blades from failing due to blade root cracks, which could lead to uncontained engine failure and damage to the airplane.
97-25-11 R1: This amendment revises an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B16 series airplanes, that currently requires disabling the remote fuel/defuel panel in the cockpit; and provides for an optional modification of the remote fuel/defuel panel, which would terminate the requirement to disable the panel. This amendment reduces the applicability of the existing AD. This amendment is prompted by reports of in-flight failure of the panel that resulted when a circuit breaker on a battery bus opened due to insufficient current flow capacity. The actions specified in this AD are intended to prevent the circuit breakers from opening during flight, which could result in irreversible loss of engine indicating and fuel quantity systems in the cockpit.
2011-23-04: We are superseding an existing airworthiness directive (AD) for the engines identified above. That AD currently requires initial and repetitive visual inspections of the forward engine mount assembly side links for cracks, stripping and reapplying the Sermetel W coating on the side links at every exposure of the side link. This new AD requires those same inspections, stripping and reapplying the Sermetel W coating, and adds two part numbers [[Page 68635]] to the applicability. This AD was prompted by a review of the inspection program, which revealed that GE had omitted two affected side link part numbers from the applicability. We are issuing this AD to prevent failure of the side links and possible engine separation from the airplane.
70-15-01: 70-15-01 SIKORSKY AIRCRAFT: Amdt. 39-1026. Applies to Sikorsky S-61A/L/N/R Type Helicopters Certificated In All Categories and Incorporating Torrington A18702 Series Cabin Heater Blower Assemblies. Compliance required within the next 25 hours' time of cabin heater operation after the effective date of this AD unless already accomplished. To prevent potential hazards associated with intermittent operation of the cabin heater blower, accomplish the following: (a) Comply with the Accomplishment Instructions (excluding paragraph D) of Sikorsky Service Bulletin No. 61B55-14 dated 1 April 1970, or later revision, or equivalent method both approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (b) Upon request with substantiation data submitted through an FAA maintenance inspector, the compliance time specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective July 22, 1970.
2021-19-01: The FAA is adopting a new airworthiness directive (AD) for certain Bell Textron Canada Limited Model 206, 206A, 206A-1 (OH-58A), 206B, 206B-1, 206L, 206L-1, 206L-3, 206L-4, 222, 222B, 222U, 230, 407, 427, 429, and 430 helicopters. This AD was prompted by a report of a shoulder harness seat belt comfort clip (comfort clip) interfering with the seat belt inertia reel. This AD requires removing each comfort clip from service, inspecting the shoulder harness seat belt for any rip and abrasion, and removing any shoulder harness seat belt from service that has a rip or abrasion. The FAA is issuing this AD to address the unsafe condition on these products.
2021-17-15: The FAA is adopting a new airworthiness directive (AD) for Leonardo S.p.a. Model AB139 and AW139 helicopters with certain main rotor blades installed. This AD was prompted by a report of an in- flight loss of a main rotor blade (MRB) tip cap. This AD requires inspecting the MRB tip cap for disbonding. The FAA is issuing this AD to address the unsafe condition on these products.
2011-23-09: We are adopting a new airworthiness directive (AD) for Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702), CL-600-2D15 (Regional Jet Series 705), [[Page 68307]] and CL-600-2D24 (Regional Jet Series 900) airplanes. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: There have been two reported cases of failure of the MLG [main landing gear] piston axle, P/N [part number] 49203-3 or 49203-5, resulting from fretting between the inboard axle sleeve and axle thrust face, damage to the protective coating and consequent stress corrosion. In both cases, the MLG did not collapse. * * * * * The unsafe condition is failure of the MLG, which could adversely affect the airplane's safe landing. We are issuing this AD to require actions to correct the unsafe condition on these products.
72-06-01: 72-06-01 BRITISH AIRCRAFT CORPORATION: Amdt. 39-1406. Applies to Model BAC 1-11 200 and 400 series airplanes which do not have BAC Modification PM 4621 Part (b) incorporated on all flap sections. Compliance is required as indicated. To prevent failures of the flap forward inboard pick-up fitting assemblies (six per airplane), accomplish the following: (a) For flap sections with a pick-up fitting assembly with a spigot having P/N AB09- 1723 (pre-Mod. 4621) installed: (1) Remove the lower inboard access panel and visually inspect the pick-up fitting assembly for failure of the spigot in accordance with British Aircraft Corporation Model BAC 1-11 Alert Service Bulletin No. 57-A-PM 4621, Issue 2, dated July 27, 1970 or an FAA-approved equivalent as follows: (i) On the inboard (No. 1) flap sections, within the next 650 landings after the effective date of this AD, or before the accumulation of 7,500 landings on the pick-up fitting assembly spigot, whichever occurs later, and thereafter at intervals not to exceed 650 landings from the last inspection until the spigot is replaced in accordance with paragraph (a)(4)(ii), or the assembly is replaced in accordance with paragraph (a)(4)(iii). (ii) On the center (No. 2) and outboard (No. 3) flap sections, within the next 2,000 landings after the effective date of this AD, or before the accumulation of 7,500 landings on the pick-up assembly spigot, whichever occurs later, and thereafter at intervals not to exceed 2,000 landings from the last inspection until the spigot is replaced in accordance with paragraph (a)(4)(ii), or the assembly is replaced in accordance with paragraph (a)(iii). (2) If a failed spigot is found during an inspection required by paragraph (a)(1), before further flight comply with paragraph (a)(4). (3) Within the next 1,000 landings after the effective date of this AD or before the accumulation of 25,000 landings on the pick-up assembly spigot, whichever occurs later, comply with paragraph (a)(4). (4) Comply with either subparagraph (i), (ii), or (iii). (i) Replace an affected spigot with a serviceable spigot of the same part number and continue to inspect in accordance with paragraph (a) (1); or (ii) Replace an affected spigot with an improved spigot, P/N AB09- 3887 (BAC Modification PM 4621, Part (a) in accordance with British Aircraft Corporation Model BAC 1-11 Service Bulletin No. 57-PM 4621, Issue 1, dated May 18, 1970 or an FAA-approved equivalent and inspect in accordance with paragraph (b)(1); or (iii) Replace the assembly containing the affected spigot with a new assembly (BAC Modification PM 4621, Part (b)) in accordance with British Aircraft Corporation Model BAC 1-11 Service Bulletin No. 57-PM 4621, Issue 1, dated May 18, 1970 or an FAA- approved equivalent. (b) For flap sections with a pick-up fitting assembly with a spigot having P/N AB09- 3887 (post-Mod. 4621, Part (a)) installed: (1) Remove the lower inboard access panel and visually inspect the pick-up fitting assembly for failure of the spigot in accordance with British Aircraft Corporation Model BAC 1-11 Alert Service Bulletin No. 57-A-PM 4621, Issue 2, dated July 27, 1970 or an FAA-approved equivalent as follows: (i) On the inboard (No. 1) flap sections, within the next 650 landings after the effective date of this AD or before the accumulation of 20,000 landings on the pick-up fitting assembly spigot, whichever occurs later, and thereafter at intervals not to exceed 650 landings from the last inspection until the assembly is replaced in accordance with paragraph (b)(4)(ii). (ii) On the center (No. 2) and outboard (No. 3) flap sections, within the next 2,000 landings after the effective date of this AD or before the accumulation of 20,000 landings on the pick-up fitting assembly, whichever occurs later, and thereafter at intervals not to exceed 2,000 landings from the last inspection, until the assembly is replaced in accordance with paragraph (b)(4)(ii). (2) If a failed spigot is found during an inspection required by paragraph (b)(1), before further flight comply with paragraph (b)(4). (3) Within the next 1,000 landings after the effective date of this AD or before the accumulation of 30,000 landings on the pick-up assembly, whichever occurs later, comply with paragraph (b)(4). (4) Comply with either subparagraph (i) or (ii). (i) Replace an affected spigot with a serviceable spigot of the same part number and continue to inspect in accordance with paragraph (b)(1); or (ii) Replace the assembly containing the affected spigot with a new assembly (BAC Modification PM 4621, Part (b)) in accordance with British Aircraft Corporation Model BAC 1-11 Service Bulletin No. 57-PM 4621, Issue 1, dated May 18, 1970 or an FAA- approved equivalent. This amendment becomes effective April 6, 1972.
2021-17-12: The FAA is superseding Airworthiness Directive (AD) 2020-13-07 for all Rolls-Royce Deutschland Ltd & Co KG (RRD) Trent 1000-D2, Trent 1000-J2, and Trent 1000-K2 model turbofan engines with a certain part- numbered fuel pump installed. AD 2020-13-07 required removal and replacement of the fuel pump with a part eligible for installation. This AD was prompted by the manufacturer's investigation into an unexpected reduction in fuel pump performance in certain high life fuel pumps and subsequent determination that an additional part-numbered fuel pump is subject to the same unsafe condition. This AD requires new and reduced life limits for certain part-numbered fuel pumps, depending on the engine model the fuel pump is installed on. The FAA is issuing this AD to address the unsafe condition on these products.